This paper presents the design calculations, implementations, and multi-engineering based computational constructions of an unmanned amphibious vehicle (UAmV) which efficiently travels underwater to detect and collect deep-sea minerals for investigations, as well as creative usage purposes. The UAmV is expected to operate at a 300 m depth from the water surface. The UAmV is deployed above the water surface near to the approximate target location and swims underwater, checking the presence of various mining, then extracts them using a unique mechanism and stores them in an inimitable fuselage location. Since this proposed UAmV survives in deep-sea regions, the design construction of this UAmV is inspired by hydrodynamic efficient design-based fish, i.e., Rhinaancylostoma. Additionally, standard analytical approaches are followed and, subsequently, the inimitable components such as wing, stabilizers, propellers, and mining storage focused fuselage are calculated. The computational analyses such as hydrodynamic investigations and vibrational investigations were carried out with the help of ANSYS Workbench. The hydrodynamic pressures at various deployment regions were estimated and thereafter the vibrational outcomes of UAmVs were captured for various lightweight materials. The computed outcomes were imposed in the analytical approach and thereby the electrical energy generations by the UAmV’s components were calculated. Finally, the hydrodynamic efficient design and best material were picked, which provided a path to further works on the execution of the focused mission. Based on the low drag generating design profile and high electrical energy induction factors, the optimizations were executed on this work, and thus the needful, as well as suitable UAmV, was finalized for targeted real-time applications.

This study focuses on establishing a conceptual design for a multirotor unmanned aerial vehicle (UAV). The objectives of this octocopter are to reduce the number of flight cancelations and car accidents owing to low-visibility issues and to improve abnormal environmental conditions due to the presence of smoke. The proposed octocopter contains a convergent–divergent [CD] duct-based storage tank, which provides a platform to store saltwater and allows it to fly in foggy zones. Fine saltwater is sprayed from the octocopter and dispersed into the low clouds, thereby altering the vapor’s microphysical processes to break it up and improve visibility. The nature of the seawater and its enhanced fluid properties, due to the involvement of octocopter, creates the fluid flow mixing between atmospheric fluids and spraying particles, which increases the settling of foggy and smokey content groundward. For deployment, the conceptual design of the octocopter was initially constructed through analytical approaches. Additionally, three unique historical relationships were created. The standard engineering approaches involved in this work were stability analysis through MATLAB and fluid-property analysis through computational fluid dynamics (CFD) cum multiple reference frame (MRF) tools. The systematic model of this octocopter was developed by CATIA, and thereafter CFD and fluid–structure-interaction (FSI) analyses were computed, in ANSYS Workbench, on the octocopter for various environmental conditions. The aerodynamic forces on the drone, the enhancement of dynamic pressure by the presence of high amounts of rotors and nozzle sprayer, suitable material to resist aerodynamic loadings, and tests on the efficiency of the controller and its electronic components were investigated in detail. Finally, the proposed octocopter-based dynamic system was conceptually constructed.

Tracking a target is an essential function of a seeker for missiles. The target tracking mechanism of a seeker consists of gimbals, mounted with gyroscopes, and an antenna or some other energy receiving devices such as radar, infrared (IR), or laser. Stabilization of such a gimbal is necessary for any guided missile to maintain the tracking device always pointing towards the target. For the stabilization of the gimbal system, several control methods have been employed for making the gimbal to follow an input rate command by eliminating all the gimbal disturbances. Here, a new self-tuning fuzzy logic-based proportional, integral, derivative (PID) controller is introduced for the stabilization of a two-axis gimbal for a manoeuvring guided missile. The proposed control method involves tuning the gains of the PID controller based on the fuzzy logic rule bases considering the missile body rotation. The performance of the stabilization loops has been verified through MATLAB simulations for fuzzy logic-based PID controller compared with the conventional PID controller. The simulation results show the response of the gimbal system with stabilization loops met the control requirements with fuzzy PID controllers but not with conventional PID controllers.

Unmanned aerial vehicles (UAVs) are gaining in popularity and sophistication in today’s modern world. UAVs are now available in a wide range of configurations. A UAV’s many applications include aerial photography and videography and target tracking. The upward-pointing propellers of some modern fixed-wing UAVs make it possible for them to take off and land vertically. Surveillance and intruder inspections are two areas where the blended wing body (BWB) configuration shines. This is because its weight is spread uniformly throughout the body, its radar signal is weaker than that of alternative configurations, and there is a relatively small amount of interference with its movement. With common design factors in mind, like vertical takeoff and landing, aerodynamic drag, and fundamental wing stability, the optimal BWB plan form for surveillance is designed. CATIA is used to finish the conceptual design of the BWB-based UAV. A fluid-structure interaction (FSI) study is carried out after the model has been examined in ANSYS Fluent. The UAV’s responsiveness is improved through simulation in the MATLAB environment after a proportional-integral-derivative-type altitude controller was developed. The results demonstrate that providing the UAV with an altitude instruction enhances its performance. Given the flexibility of the suggested BWB UAV’s design, we have decided to limit its maximum forward speed to 75 m/s and its maximum rate of vertical ascension to 50 m/s. Rapid BWB UAVs like the one seen here are quite helpful in dangerous situations.

In guided missiles, the major function of a seeker is to track a target continuously. In target tracking process most seekers employ a gimbal system, usually a two-axis, on which a tracking device and a rate gyroscope are mounted. For such guided missiles, the stabilization of gimbal is essential for maintaining the tracking device directing towards the target. Various control methods have been developed for the gimbal stabilization to make the gimbal to respond faster for a rate command input so that the gimbal follows the rate input in the presence of disturbances. Here, a fuzzy self-tuning proportional, integral, derivative (PID) type controller based on parameters adaptive method is proposed for two-axis gimbal stabilization which can be applicable for most guided missiles. The controller gains in the proposed control technique are made of input and output scaling factors used in fuzzification and defuzzification processes. The scaling factors are tuned online based on the missile rotation rate and the gimbal rate response. The response of the gimbal in the stabilization loop with the proposed controller has been analyzed in MATLAB for various missile rotation rates and the simulation results are compared with a traditional PID controller. The results prove the efficiency of the proposed control method which gives a better and faster response with zero steady-state error than the traditional control method.

In recent years, multirotor unmanned aerial vehicles (MRUAVs) have seen increased investment and deployment for various novel uses, including intruder surveillance, agro farming, and crack detection in severe environments. An identical line of inquiry motivates this work, which aims to better use MRUAVs for agriculture. This study used an agricultural drone (AD) with a coaxial propeller. The proposed AD has increased stability compared to conventional ADs due to employing a coaxial rotor instead of one of the conventional rotors. The proposed AD can be customized to accommodate a wide range of design requirements; however, this investigation uses a payload weight of 2.5 kg. The coaxial propeller arrangement, the “Y” frame, and the fertilizer tank are among the many complex AD parts built efficiently with the help of the cutting‐edge tool CATIA. Predictions of flow behavior over the AD and its side effects are presented to confirm the built AD further. Eddy formation and the subsequent pressure drag developments on the AD are simulated using the province computational tool Ansys Fluent. Velocity profiles of fluid variations over the AD are studied after estimating vertical takeoff, vertical landing, and forward speed conditions for various flexible payloads equipped with MRUAV models. The AD’s minor influence allows the construction of eddy structures within and around it. Finally, AD’s structural displacements and failure factors under aerodynamic loads are commuted through the fluid‐structure interaction approach. The suggested agricultural drone, thus, is robust and well suited for multicomputational tool agricultural applications.